Hostname: page-component-848d4c4894-cjp7w Total loading time: 0 Render date: 2024-06-15T17:47:39.100Z Has data issue: false hasContentIssue false

Two and Three-Dimensional Potential Flow by the Method of Singularities*

Published online by Cambridge University Press:  04 July 2016

J. H. Argyris
Affiliation:
Imperial College of Science and Technology, University of London Institut für Statik und Dynamik der Luft- und Raumfahrtkonstruktionen, Universität Stuttgart
D. W. Scharpf
Affiliation:
Imperial College of Science and Technology, University of London Institut für Statik und Dynamik der Luft- und Raumfahrtkonstruktionen, Universität Stuttgart

Extract

A very simple technique for the computation of two-and three-dimensional potential flows, based on the method of singularities, has been initiated by A. M. O. Smith and his collaborators and developed by them into a successful standard procedure at Douglas. The program assumes a representation of the immersed body by straight respectively planar facets or elements on each of which a constant source distribution is taken to act. The associated velocity field is easily established and the intensity of the sources determined from the boundary condition of zero normal velocity in the compound flow. It appears reasonable to expect a higher degree of accuracy by the adoption of a more sophisticated source distribution and the use of curved surface elements which allow a better approximation to the actual geometry. Experience in structural analysis has clearly shown that the gain in accuracy achieved by more elaborate elements increases at a higher rate than the corresponding programming effort.

Type
Technical Notes
Copyright
Copyright © Royal Aeronautical Society 1969 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Footnotes

*

This and the following Technical Notes are Appendices I and II to the Lanchester Memorial Lecture which is to be printed in two parts in the January and February issues of The Aeronautical Journal, where all references will be given in full.

References

* This and the following Technical Notes are Appendices I and II to the Lanchester Memorial Lecture which is to be printed in two parts in the January and February issues of The Aeronautical Journal, where all references will be given in full.